Method for managing and representing a rate of turn indicator for an aircraft

1. A method for managing and representing a rate of turn indicator for an aircraft implemented by an avionics system on board an aircraft, the avionics system comprising: a first sensor to determine the angles of inclination in roll and in pitch of the aircraft; a second sensor to measure the specific speed of the aircraft; an electronic computer; a display comprising a visualization device arranged in such a way as to display at least one line called horizon line, the inclination of which represents the angle of inclination of the aircraft and an airplane model symbol, the position of which with respect to the horizon line represents the attitude of the aircraft; a storage component comprising at least a first predetermined value of a specific speed of the aircraft and a second predetermined value of an angle of inclination associated with the first value, these two values defining the standard rate of turn allowing the aircraft to carry out a turn during a predetermined time period; wherein an operation of computing and graphically representing the airplane model symbol is arranged in such a way that the graphic representation of the airplane model symbol is a function of the specific speed of the aircraft and of the angle of inclination, wherein the airplane model symbol comprises at least two straight arms of equal length, interlinked by a common point and inclined to the horizontal symmetrically in such a way as to form an inverted V; and wherein the angle of inclination of one of the two arms of the V is proportional to the specific speed of the aircraft, the coefficient of proportionality being determined in such a way that when the specific speed and the angle of roll correspond to the first value and to the second value of the standard rate, the arm is parallel to the horizon line, thus indicating that the aircraft is carrying out its turn at the standard rate.

2. A method according to claim 1 , wherein, the angle of inclination of the arms of the V being expressed in degrees, the speed being expressed in knots, the coefficient of proportionality has a value of substantially 0.15 degrees/knot.

3. A method according to claim 2 , wherein the general shape of the model is a symmetrical chevron including two upper bars and two lower bars, the two upper bars being the two arms of the model.

4. A method according to claim 1 , wherein the storage component comprises at least a third predetermined value defining a maximum authorized inclination, and the avionics system further comprises a sonic alarm that, when the maximum inclination is reached, an alerting operation is triggered during which the sonic alarm is activated and the airplane model symbol becomes red.

5. A method according to claim 4 , wherein the general shape of the model is a symmetrical chevron including two upper bars and two lower bars, the two upper bars being the two arms of the model.

6. A method according to claim 1 , wherein the general shape of the model is a symmetrical chevron including two upper bars and two lower bars, the two upper bars being the two arms of the model.